Aeroplane.



T. BOLLIN.

AERUPLANB.

AFPLIOATIQN FILED SEPT. 23, 1912.

1,1 17,315., y Patented Nov. 17, 1914.

4 SHEETS-SHEET 1.

Tl BOLLIN.

AEROPLANE.

APPLICATION FILED SEPT. 23, 1912.

Patented NW1?, 1,914@

4 SHEBTS-SHEET 2.

Lll.,

T. BOLLIN. ABROPLANB. APPLIOATIO-N FILED SEPT. 23. 1912.

LE, 17,315, I A Patented NOV.17,1914.

4 sums-SHEET 3.

T. BOLLIN.

AEROPLANE.

APPLIOATION FILED sBPT.23,1912.

1,1 17,31 5. Patented Nov. 17, 1914.

4 SHEETS-SHEET 4.y

waffe unrrnn sacarme ramena crimen.

THE-ODORE BOLLIN', OF KANSAS CITY, MISSOURI.

AEROPLANE.

1,1 rusia.

To all whom it may concern.'

veliminate or reduce to the minimum, the

danger attendant upon `the descent of the machine to the ground. Q

lVith this general oblect 1n view and others as hereinafter appear, theinvention consists in certain novel-and peculiar features ofconstruction and organization as hereinafter described and claimed; andin order that it may .befully understood reference is to be had to theaccompanying` drawings, in whichfn Figure 1, is a side elevation of anaeroplane embodying my invention. Fig. 2, is a front view of the same.Fig. 3, is a top plan View of the same. lai-ged front elevation of thecontrol mechanism. Fig. 5, is a section on the line V-V of F ig. 4. Fig.6, is a fragmentary perspective view of the main plane and an auxiliaryfolding plane. Fig. 7, is a horizontal section showing means whereby theailerons of the machine are operated. .F ig. 8, is a detail showingcertain cables.

In the said drawings where likel reference characters identifyAcorresponding parts in all the figures, l is the main plane of themachine, the same corresponding substantially in form and arrangement tothe upper plane of the biplanes in common use, and underlying'biitnarrower and shorter than said plane, is a substantially lsimilar planeQ, the same beingbf less area than plane 1, for the purpose ofcentralizing the weight below the middle of the main plane. Theplanesnear their front margins are connected by the customary struts 3,similarstruts 4 connecting the rear portions of plane y2 with plane l, somedistance forward of its rear Fig. 1, is an en-.

Specifcationcf Letters Patent. v Patented NDV. 1HE., 191.4. Applicationfiled September 23, 1912. Serial No. 721,945.

margin. Each set of said struts is braced by crossed wires 5, crossedwires ,G lbeing also employed' between the two sets of struts.

Two of the rear struts Ll at `a suitable distance apart a-id' equal'distances from the longitudinal center of the planes, are provided withdepending extensions 7, and projecting forwardly from the lower ends ofthe same are longitudinal bars 8, which curve nl wardly at their4 frontends by preference, yo accommodate the machine to irregulaiitiesgfan thesurface of the ground in its travel thereon preliminary and subsequentto Amaking a flight, and said bars are heldfreliably' in placebydownwardly and forwardly extending bars '9, and inclined braces `10Springs l1 are mounted upon the bars 8, and carry suitably journaledwheels 12, upon which are supportedl the front end of the machine whenon the ground.

The fuselage of the machine, which eX tends longitudinally as iscustomary, consists of a front portion 13 and a rear portion 14 in fixedrelation to the planes, and pivoted to the lfront end of portion 13 formovement in a vertical plane, isa horizont-al rudderl, equipped with.upwardly and downwardly projecting arms 16 and 17.' The sides of therear portion of the fuselage converge rearwardly by preference,-and neartheir rear ends are connected by a cross bar 1S, upon which is pivotedfor lateral movement, the vertical rudder 19, and said rudder isprovided with oppositely projecting arms Q0 and 21.

is a cross bar mounted on the rear portion of the fuselage, and securedto theends of the same and to the fuselage in any suitable manner, arestabilizing planes 23, and located rearward of said cross bar and atopposite sides of the fuselage and hinged at 24e to the former for upand down movement, are horizontal rudders 25, provided with upvardly-projecting arms 2G, and depending arms 2'7, thenipwardlyprojecting arms being connected by a. cross bar 28 above and thedepending arms by a cross bar 29 underlying the fuselage, suitableinclined braces 30 extending from the rear portions drums are cables 74which extend forwardly and rearwardly from said drums. The foi'- wardlyextending portions of said cables engage guide sheaves 75 and 76 carriedby the fuselage, and then extend around guide sheaves 77 secured to theends of frames 36,

and from said guide sheaves 77 extend rear` wardly and are attached tothe ends of bar al, as shown most clearly in Fig. 6. Therearwardly-extending portions of cables 7l, extend around guide sheaves7S and 79, and from the latter extend upwardly and around guide sheaves80, secured to the rear corners underlying plane 2, act like a parachutein:y

guarding against overturning of the inachine in its descent if beyondthe control of the operator, it being understood that should theoperator lose control, that he will immediately open these curtains orauxiliary planes to accomplish the result mentioned, and that when themachine is under control the curtains or auxiliary planes will be infolded coildition.

Projecting from the rear edge of plane 1, near the outer ends thereof,is a pair of ailerons 8l, which under normal conditions occupy a neutralor substantially horizontal position, and each is connected by a cable82 guided around sheaves S3 and 84 suitably supported from the rearportion of the fuselage, to a separate lever 85 fuleruined at SG on oneof the standards 4-9, and for the purpose of operating the right handaileron when the vertical rudder is turned in that direction, and theleft-hand aileron when said rudder is turned to the left, the shaft isequipped with a crank 87a having' the rigid cui-ved arms 87 and S8 torespectively operate the left or righthand lever S5. Iny thisarrangement one of the ailerons assists in turning the machine and,

1 because it is swung downward, assists in sustaining the machine duringthe turning movement, it being understood thatthe ailerons are, duringllight, supported in horizontal position by the action of the air, sothat the levers S5 are held normally against the arms S7 and S8, andshould the vertical rudder be incapacitated for service, the np.-`eration of the steering wheel 61, in the lifegular way, will result inturning the machine in the desired direction because only oie aileron ata time is adjusted to an angle to the line, of flight, the otherretaining its neutral orinoperative position.

i The engine 89 is suitably supported on the longitudinal axis of themachine forward and within the reach of the operator, and is connectedin any well known manner (not shown) to a pair of propellers 90, thoughone propeller may be employed if desired.

From the above description it will be apv parent that I have produced anaeroplane possessing the features of advantage enu nierated asdesirable, and I wish it to' be understood that I do not desire to berestricted to the exact details of construction shown and described, butreserve the right to make all changes properly falling within the spiritand scope of the appended claims.

I claim: p

l. In an aeroplane, an upper main plane and a plane below and spacedfrom and of smaller area than the upper plane, in com- .,bination with`planes forward and rearward of and in substantially the saine plane asthe said main plane; said forward and rearward planes being foldingplanes and substantially shorter transversely than the main yplane andwhen unfolded forming in conjunction with t'he main plane an unbroken orcontinuous cross-shaped plane. j

2. In an aeroplane, an upper main plane andv a plane below and spacedlfrom and of smaller area than the upper plane, in combination withplanes forward and rearward of and iii substantially the sameplane asthe said main plane, said forward and rear ward` planes being foldingplanes and sub stantially shorter transversely than the main plane andwhen unfolded foriniiigfin conjunction with the main plane an unbrokenor continuous cross-shaped plane, and means for simultaneously unfoldingsaid planes.

3. An aeroplane, comprising an upper or main plane of greatest lengthtransversely, a smaller plane below the first-named plane, a fuselageextending atright angles to said planes, a horizontal and avertical'rudder mounted on they fuselage, a pair of frames insubstantially the saine plane as the firstnained plane and forward andrearward thereof, folding planes carried by said. frames and adaptedwhen in open or operative position to bridge the spaces between saidmain plane and the ends of said frames,

and when closed or in inoperative position to leave said spacesunbridged, connections between said folding planes to transmit mo" tionfrom one to the other, a shaft, a pair of drums upon` the shaft, and acable secured .to each drum, said cables being connected at their rearends to one of the folding planes ailid at their front ends to the otherfolding p ane. y

4. An aeroplane, comprising a fuselage, a plane extending transverselyofthe fuselage at both sides thereof, a vertical rudder at the rear end ofthe fuselage, a pair of ailerons projecting rearwardly from the ini Fur,in die presence of two Witnesses.

`THEDRE BULMIN. Witnesses:

C. RoDGERsg' G. Y1 THOBPE.

@www @E if# @h'aimd im five cents each, by addressing the Commissionerof latems.

Washngw, El G.

